Integrated design method of backpack type double-air-inlet-channel aircraft forebody

Abstract

The invention relates to an integrated design method of backpack type double-air-inlet-channel aircraft forebody which comprises the following steps: (1) designing a shock wave curve and an aircraft forebody lower surface characteristic curve, and generating an aircraft forebody lower surface; (2) designing a characteristic curve of the upper surface of the aircraft along a flow direction and a spanwise direction, and generating an aircraft forebody upper surface; (3) designing two-dimensional characteristic curves of air inlet inlets distributed on two sides of the center line of the aircraftforebody, and projecting the two-dimensional characteristic curves to the upper surface of the aircraft forebody generated in the step (2) to obtain an air inlet three-dimensional inlet curve; and (4) according to the three-dimensional inlet curve of the air inlet channel obtained in the step (3), carrying out streamline tracking in the corresponding conical flow field to obtain an inner flow channel of the air inlet channel. While the advantages of the waverider aircraft forebody are kept, the design of the hypersonic air inlet channel is carried out on the upper surface of the aircraft in asymmetrical mode, so that the aerodynamic performance of a propulsion system is improved while the high performance of the waverider aircraft forebody is exerted, and a new method is provided for internal and external flow integrated design.

Description

Technical field [0001] The invention relates to the technical field of integrated design of a front body and an air inlet, in particular to an integrated design method for the front body of a backpack-type dual air intake aircraft. Background technique [0002] In the field of hypersonic vehicle design, the air-breathing propulsion system has the advantages of simple structure, high specific impulse, and low failure rate. For a long time, it has been the first choice for the design and development of hypersonic aircraft. Although the air-breathing propulsion system has the above advantages, studies have proved that after matching the aircraft body, both the propulsion system and the aerodynamic performance of the aircraft body will be greatly affected. Therefore, the key problem that needs to be solved in order to achieve hypersonic flight is the integrated design of the aircraft body and the propulsion system, and the most difficult problem is the integrated design of the aircra...

AI Technical Summary

Problems solved by technology

Lewis pointed out in the literature that although the perfect waveriding theory can help us easily design an aircraft with a lift-to-drag ratio of 7-8, the existing hypersonic aircraft with a matching engine has a maximum lift-to-drag ratio of only 3.8

It can be seen that the key problem restricting the overall performance of the hypersonic system at present is the lack of an integrated design method suitable for the aircraft precursor and the inlet

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